Turbine bladed with tip cooling
A turbine blade with a blade tip cooling passage formed within the blade tip and extending from the leading edge to the trailing edge. The blade tip passage includes a plurality of fins extending from the pressure side to the suction side walls of the passage, and in which each fin includes a cooling air opening, the openings of which alternate from the pressure side to the suction side in the passage to force the cooling air to flow in a sinusoidal manner. The openings also alternate from the bottom of the passage to the top of the passage so that the cooling air flows in a spiral shape manner. Film cooling holes are positioned along the pressure side walls for some of the spaces formed between adjacent fins to provide film cooling for the blade. A leading edge cooling supply channel supplies cooling air to the blade tip passage through a metering and impingement hole in the first space of the passage located on the leading edge. The fins with the alternating pattern of openings produce both impingement cooling and vortex cooling for the blade tip.
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1. Field of the Invention
The present invention relates generally to fluid reaction surfaces, and more specifically to turbine blade with a cooling circuit in the blade tip.
2. Description of the Related Art Including Information Disclosed Under 37 CFR 1.97 and 1.98
In the prior art, blade tip cooling is accomplished by drilling holes into the upper extremes of the serpentine flow coolant passages from both the pressure and suction side surfaces near the blade tip edge and the top surface of the squealer cavity. The cooling flow distribution and pressure ratio across these film cooling holes for the airfoil pressure and suction sides as well as the tip region is subject to severe secondary flow field, which translates into a large quantity of film cooling holes and cooling flow that is required for cooling the blade tip peripheral.
It is an object of the present invention to provide for a blade tip cooling circuit that will provide adequate blade tip cooling with less cooling air flow.
It is another object of the present invention to provide for a turbine blade with a blade tip cooling circuit that provides both impingement cooling and vortex flow cooling for the blade tip circuit.
BRIEF SUMMARY OF THE INVENTIONThe present invention is a turbine blade with a blade tip cooling circuit formed between a tip ceiling and tip floor and the pressure side and suction side walls of the blade that forms a blade tip passage extending from the leading edge to the trailing edge of the tip. A cooling air supply hole is located in the tip floor to supply cooling air to the passage. A plurality of fins extend across from pressure side to suction side in the passage and have an opening in the corners that alternate from the pressure side to the suction side and allow the passage of the cooling air. The openings in the fins also alternate from the tip floor to the tip ceiling for the passage of the cooling air. Film cooling holes on the blade pressure side wall between each of the fins discharge cooling air from the blade tip passage to the airfoil surface. This alternating arrangement of fins provides for an impingement plus vortex cooling flow in the blade tip.
The turbine blade with the blade tip cooling circuit of the present invention is shown in
The main feature of the present invention is the cooling circuit located within the tip cap of the blade and shown best in
The openings in the fins also alternate from the tip floor to the tip ceiling as seen in
In
Operation of the cooling flow circuit of the present invention is now described. Pressurized cooling air enters the blade root in each of the three cavities located in the blade root as seen in
The cooling air that passes through the supply hole 22 will then flow through the opening 25 in the first fin 23, and then spiral around the tip cap passage through the alternating arrangement of openings in a spiral-like flow. In each of the spaces between adjacent fins, if a film cooling hole 31 is present some of the cooling air flow will pass through the film cooling hole 31 to provide film cooling for the pressure side tip edge of the blade. As the spirally cooling air flows through the tip cap passage, film cooling air is diverted out from the blade until the cooling air enters the last space in the tip cap passage and exits the blade through the last film cooling hole 31.
In the present invention, the blade tip could include a squealer tip formed above the tip cap cooling circuit with the alternating fins 23 and 24 and openings 25. The tip cap cooling flow circuit can also be compartmentalized for tailoring the gas side pressure distribution. The convective cooling air is then channeled from the blade mid-chord serpentine flow circuit 12 or the trailing edge flow circuit 14 and into the blade tip section through an additional cooling air supply hole to form impingement plus serpentine channels to form the spiral shaped cooling air flow through the circuits.
The advantages of the blade tip cooling circuit of the present invention are as follows. Reparability of the blade tip treatment—any blade tip treatment layer can be stripped and re-applied without the possibility of hole plugging or the difficulty of re-opening tip cooling holes. Elimination of blade tip drilling holes—since the entire cooling scheme can be cast into the airfoil, drilling cooling holes on top of the blade squealer floor can be eliminated, which will reduce the blade manufacturing cost and improve the blade life cycle cost. Elimination of blade core print out hole—the horizontal cooling channel and the metering hole can be used as the blade core print out hole. Elimination of the welding of the core print out holes is this accomplished. Also, this integral blade tip cooling scheme will prevent core shift by inter-connecting the horizontal channels. Enhancing coolant flow—compartment of the horizontal cooling channel can also be incorporated into the current cooling concept which allows each individual cooling channel to be tailored for tip cooling flow to the various supply and discharge pressures around the airfoil tip. Higher overall blade tip cooling effectiveness—since coolant air is used first to cool the blade top surface by means of impingement plus vortex channel convection cooling and then discharges into the airfoil surface as film cooling. A higher heat transfer coefficient is generated by the vortex flow mechanism in the horizontal flow channel, yielding a cooler blade tip. This double usage of cooling air improves the overall cooling efficiency.
Claims
1. A turbine blade for use in a gas turbine engine, the turbine blade comprising:
- a cooling air supply channel extending from the blade root to the blade tip to supply cooling air to the blade tip;
- a blade tip cooling air passage formed between a pressure side wall and a suction side wall of the blade;
- a plurality of fins extending between the pressure and the suction side walls of the blade tip cooling air passage;
- at least some of the fins having a cooling air opening located on the pressure side half of the fin; and,
- at least some of the fins having a cooling air opening on the suction side half of the fin.
2. The turbine blade of claim 1, and further comprising:
- at least some of the fins have the opening on the floor side of the fin; and,
- at least some of the fins have the opening on the ceiling side of the fin.
3. The turbine blade of claim 1, and further comprising:
- at least some of the spaces formed between adjacent fins include a film cooling hole to discharge cooling air from the blade tip cooling air passage and onto the external surface of the blade.
4. The turbine blade of claim 2, and further comprising:
- the series of openings form substantially a spiral shaped flow passage through the blade tip cooling air passage.
5. The turbine blade of claim 1, and further comprising:
- the cooling air supply channel is a leading edge channel; and,
- a metering and impingement hole located in the tip floor provides for the cooling air connection between the supply channel and the blade tip cooling air passage.
6. The turbine blade of claim 1, and further comprising:
- the blade tip cooling air passage is a closed cooling air passage extending substantially from the leading edge to the trailing edge of the blade tip except for the cooling supply hole and the film cooling holes.
7. The turbine blade of claim 1, and further comprising:
- the ceiling of the blade tip cooling passage forms a floor for a squealer tip cavity.
8. The turbine blade of claim 6, and further comprising:
- the fins extend from the leading edge to the trailing edge of the blade tip; and,
- the cooling air openings alternate from pressure side to suction side of the passage, and from floor to ceiling of the passage to produce a spiral shape cooling air path.
9. The turbine blade of claim 8, and further comprising:
- most of the spaces formed between adjacent fins include a film cooling hole to discharge cooling air to the external surface of the blade.
10. The turbine blade of claim 8, and further comprising:
- the cooling air openings are of various sizes in order to regulate the cooling air pressures and flows through the passage and the film cooling holes.
11. The turbine blade of claim 1, and further comprising:
- the fins and the cooling air openings produce both an impingement cooling and a vortex cooling for the blade tip.
12. A process for cooling a blade tip of a turbine blade, the turbine blade having a cooling air supply channel extending from the blade root to the blade tip, the process comprising the steps of:
- metering at least some of the cooling air from the cooling supply channel into the blade tip;
- passing the cooling air in the blade tip in an alternating manner from pressure side to suction side of the blade tip; and,
- discharging cooling air through film cooling holes along the blade tip as the cooling air passes toward the trailing edge of the blade.
13. The process for cooling a blade tip of a turbine blade of claim 12 above, and further comprising the step of:
- the step of passing the cooling air in the blade tip in an alternating manner from pressure side to suction side of the blade tip also includes passing the cooling air in an alternating manner from the tip floor to the tip ceiling such that a spiral shape flow path is formed within the blade tip.
14. The process for cooling a blade tip of a turbine blade of claim 12 above, and further comprising the step of:
- the step of metering at least some of the cooling air from the cooling supply channel into the blade tip includes impinging the cooling air into the blade tip to provide impingement cooling for the squealer tip.
15. The process for cooling a blade tip of a turbine blade of claim 14 above, and further comprising the step of:
- the steps of metering and impinging the cooling air into the blade tip include passing the cooling air along a leading edge channel to provide cooling to the leading edge portion of the blade before metering the cooling air into the blade tip.
4411597 | October 25, 1983 | Koffel et al. |
4606701 | August 19, 1986 | McClay et al. |
5660523 | August 26, 1997 | Lee |
5738491 | April 14, 1998 | Lee et al. |
5997251 | December 7, 1999 | Lee |
6027306 | February 22, 2000 | Bunker |
6164914 | December 26, 2000 | Correia et al. |
6916150 | July 12, 2005 | Liang |
6932571 | August 23, 2005 | Cunha et al. |
6971851 | December 6, 2005 | Liang |
7334991 | February 26, 2008 | Liang |
Type: Grant
Filed: Mar 6, 2007
Date of Patent: May 11, 2010
Assignee: Florida Turbine Technologies, Inc. (Jupiter, FL)
Inventor: George Liang (Palm City, FL)
Primary Examiner: Igor Kershteyn
Attorney: John Ryznic
Application Number: 11/715,048
International Classification: F01D 5/18 (20060101);